TY - JOUR
T1 - Influence of blade tip clearance at near-stall condition on transonic axial-flow compressor
AU - Xie, Fang
AU - Chu, Wu Li
AU - Li, Xiang Jun
AU - Liu, Chuan Le
PY - 2014/10/1
Y1 - 2014/10/1
N2 - Numerical simulation with high density grid was carried out to study blade tip clearance of a transonic axial-flow compressor rotor 37 at near-stall condition. The blade tip clearance included design clearance, half design clearance, quarter design clearance, 2 times design clearance and zero clearance. The results show that stall margin is improved 4%, and adiabatic efficiency and pressure ratio don't decline obviously, when the blade tip clearance reduced from design clearance to half design clearance. Details of the flow field were analyzed based on different stall forms and vortex dynamics. The change of clearance may improve stability margin greatly and clearance plays an important role in leakage vortex and separation of boundary layer, or even induces different stall forms. This has provided necessary basic research for design of the compressor are provided, and discussed the application condition of clearance control technology in aerodynamics.
AB - Numerical simulation with high density grid was carried out to study blade tip clearance of a transonic axial-flow compressor rotor 37 at near-stall condition. The blade tip clearance included design clearance, half design clearance, quarter design clearance, 2 times design clearance and zero clearance. The results show that stall margin is improved 4%, and adiabatic efficiency and pressure ratio don't decline obviously, when the blade tip clearance reduced from design clearance to half design clearance. Details of the flow field were analyzed based on different stall forms and vortex dynamics. The change of clearance may improve stability margin greatly and clearance plays an important role in leakage vortex and separation of boundary layer, or even induces different stall forms. This has provided necessary basic research for design of the compressor are provided, and discussed the application condition of clearance control technology in aerodynamics.
KW - Clearance leakage flow
KW - Separation of boundary layer
KW - Shock wave
KW - Stability margin
KW - Transonic axial-flow compressor
UR - http://www.scopus.com/inward/record.url?scp=84910060986&partnerID=8YFLogxK
U2 - 10.13224/j.cnki.jasp.2014.10.019
DO - 10.13224/j.cnki.jasp.2014.10.019
M3 - 文章
AN - SCOPUS:84910060986
SN - 1000-8055
VL - 29
SP - 2417
EP - 2423
JO - Hangkong Dongli Xuebao/Journal of Aerospace Power
JF - Hangkong Dongli Xuebao/Journal of Aerospace Power
IS - 10
ER -